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The general bad economic situation, especially the plight of the aviation industry, hardly allows us to develop anything other than training and touring aircraft.
It can therefore hardly be disputed that we do not currently have a sports aircraft for the demanding aviator in Germany, although a certain interest in this cannot be denied. We are therefore publishing the following draft in order to provide inspiration for new types.
The following aspects were decisive in the development of the project: favourable aerodynamic training, smallest dimensions, contemporary
horizontal speed and good climbing performance. Since we do not have a large selection of aircraft engines in Germany, the 4-cylinder Hirth engine HM 60 was provided as a power source, whose peak power of 70 hp can be used. In order to
achieve the lowest possible weights, and since the biplane offers no advantages for an aircraft with such a small area, the braced high-wing aircraft was chosen.
Hull with oval cross-section made entirely of plywood. The two main frames are pulled together upwards and, with a
streamlined cladding, which is stiffened, form the attachment points of the two-part, two-spar wing. The rear edge of the streamlined body is cut off vertically near the rear wing. The resulting vertical surface houses the flight measuring instruments, which the guide has directly in front of him at eye level.
The wing is planked with plywood up to the rear spar, the rear wing part is covered with fabric. Incidentally, the wing is supported by V-struts after the fuselage. The horizontal stabilizer is two-part, hinged to the fuselage and braced with wires after the fuselage and the side fin. The elevator and side fin are planked with plywood, the rudders are clothed and not balanced. The elevator fin can be adjusted at the stand by means of a centrally located wing screw.
The chassis struts are made of wood and consist essentially of a spar that grows organically out of the main frame. Glued to this spar and the lower fuselage spar is a plywood panel, which is stiffened by ribs and at the end by molded strips glued on the sides. This entire skeleton is planked with plywood, giving it a streamlined shape. A comprehensive fitting is applied to the lower, strongly tapered end, at the end of which a sleeve is welded into which the axle of the impellers is slid. Dun-Iop low-pressure tires are planned as wheels, the dimensions are 430 mm & and 155 mm wide. The entire impact forces are absorbed by the tires. The wingspan of the chassis is 1.5 m.The
fuel and oil tanks are located in the centre of gravity of the machine and have a capacity for a flight time of 2 hours.Setup
weight 245 kg, payload 115 kg, flight weight 360 kg, maximum length approx. 5.7 m, maximum height approx. 1.8 m, wingspan 7.5 m, wing depth 1.3 m, wing area 9 m2,
wing loading 40 kg/m2, Power load 5.14 kg/hp, area output 7.7 hp/m2.
Horizontal speed near the ground 216 km/h, cruising speed 192 km, landing speed 76 km, climb time to 1000 m 3.8 min. Summit altitude approx. 7000 m.